SEMIEMPIRICAL AIRFRAME NOISE PREDICTION MODEL AND EVALUATION WITH FLIGHT DATA

A semiempirical maximum overall sound pressure level (OASPL) airframe noise model was derived. Noise radiated from aircraft wings was modeled on the trailing edge diffractes quadrupole sound theory. The acoustic dipole sound theory was used to model noise from the landing gear. The model was correlated with maximum OASPL flyover noise measurements obtained for three jet aircraft. One third octave band sound pressure level flyover data was correlated and interpreted.

• Corporate Authors:

  NASA Dryden Flight Research Center

  P.O. Box 273
  Edwards, CA  United States  93523-0273
• Authors:
  • Hersh, A S
  • Burcham, FWJ
  • Putnam, T W
  • Lasagna, P L
• Publication Date: 1976-12

Media Info

• Pagination: 36 p.

Subject/Index Terms

• TRT Terms: Acoustic measuring instruments; Acoustics; Aerodynamic noise; Aircraft wings; Airframes; Diffraction; Effective sound pressure; Flight characteristics; Forecasting; Landing gear; Mathematical models; Mathematical prediction; Measurement; Noise; Performance; Trailing edges
• Uncontrolled Terms: Noise measurement; Performance prediction
• Old TRIS Terms: Acoustic measurement
• Subject Areas: Aviation; Environment; Vehicles and Equipment;

Filing Info

• Accession Number: 00154333
• Record Type: Publication
• Source Agency: National Technical Information Service
• Report/Paper Numbers: NASA-TM-X-56041, H-951
• Contract Numbers: NAS4-2250
• Files: TRIS
• Created Date: May 31 1977 12:00AM